[elmo555]

Originally Posted by K31th

Hi Felix,

I did the same way as you ( plot3dToFoam and autoPatch on NASA mesh), however i face the problem of the airfoil has a flat plate coming out of the trailing edge and it extends all the way to the outlet.

I wonder if i miss out any step in between ?

For me, the following procedure to use PLOT3D meshes from NASA works well:

1. Download your 2D mesh from NASA and put the file in your case folder
2. Create mesh: plot3dToFoam -noBlank -2D 1 n0012_897-257.p2dfmt
3. Extract 5 patches (auto0-auto4): autoPatch -overwrite 45
4. Rename patches to a easily readable form: createPatch -overwrite

You'll need a createPatchDict for the last step, I attached the one I'm using.

[isaac1326]

Originally Posted by elmo555

For me, the following procedure to use PLOT3D meshes from NASA works well:

1. Download your 2D mesh from NASA and put the file in your case folder
2. Create mesh: plot3dToFoam -noBlank -2D 1 n0012_897-257.p2dfmt
3. Extract 5 patches (auto0-auto4): autoPatch -overwrite 45
4. Rename patches to a easily readable form: createPatch -overwrite

You'll need a createPatchDict for the last step, I attached the one I'm using.

I am still getting the flat plate, how to remove the plate? I have used 897X257 (513 points on airfoil surface) link. Both the 2D and 3D are giving me such errors

[afa13]

Originally Posted by FelixL

Hello James,


you can see you individual boundary patches in paraView by selecting and deselecting them in the patch-tree (don't know how it's called right now) in paraView. Then you should see the mishap with the boundary patch definition.

As for resolving the problem: that's up to you or someone, who is familiar with pointwise. I used the OF Tools plot3dToFoam and autoPatch to convert the NASA meshes, but the procedure is difficult to explain. Just play with the OF provided tools and you'll find your own procedure. Since you are a beginner with OF, it doesn't hurt to get to know the mesh utilities.


Greetings
Felix

Hey Felix,


I am having the same issue as James. I am doing the exact same thing but I'm not getting the values can you please help me figure it out? I used plot3d and autopatch using the file provided by NASA. The following is the checkmesh results and below is the case I'm working on:

/*---------------------------------------------------------------------------*\
  =========                 |
  \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox
   \\    /   O peration     | Website:  https://openfoam.org
    \\  /    A nd           | Version:  8
     \\/     M anipulation  |
\*---------------------------------------------------------------------------*/
Build  : 8
Exec   : checkMesh
Date   : Apr 23 2021
Time   : 15:31:09
Host   : "vm"
PID    : 48158
I/O    : uncollated
Case   : /home/cfd/OpenFOAM/cfd-8/run/nutilda-Nasa
nProcs : 1
sigFpe : Enabling floating point exception trapping (FOAM_SIGFPE).
fileModificationChecking : Monitoring run-time modified files using timeStampMaster (fileModificationSkew 10)
allowSystemOperations : Allowing user-supplied system call operations

// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //
Create time

Create polyMesh for time = 0

Time = 0

Mesh stats
    points:           115648
    internal points:  0
    faces:            229856
    internal faces:   114208
    cells:            57344
    faces per cell:   6
    boundary patches: 5
    point zones:      0
    face zones:       0
    cell zones:       0

Overall number of cells of each type:
    hexahedra:     57344
    prisms:        0
    wedges:        0
    pyramids:      0
    tet wedges:    0
    tetrahedra:    0
    polyhedra:     0

Checking topology...
    Boundary definition OK.
    Cell to face addressing OK.
    Point usage OK.
    Upper triangular ordering OK.
    Face vertices OK.
    Number of regions: 1 (OK).

Checking patch topology for multiply connected surfaces...
    Patch               Faces    Points   Surface topology                  
    outlet              256      514      ok (non-closed singly connected)  
    front               57344    57824    ok (non-closed singly connected)  
    back                57344    57824    ok (non-closed singly connected)  
    airfoil             256      512      ok (non-closed singly connected)  
    inlet               448      898      ok (non-closed singly connected)  

Checking geometry...
    Overall domain bounding box (-484.457 -1 -507.806) (501 0 507.806)
    Mesh has 2 geometric (non-empty/wedge) directions (1 0 1)
    Mesh has 2 solution (non-empty) directions (1 0 1)
    All edges aligned with or perpendicular to non-empty directions.
    Boundary openness (3.56356e-19 -1.77038e-15 -4.21148e-19) OK.
 ***High aspect ratio cells found, Max aspect ratio: 2.98998e+07, number of cells 7320
  <<Writing 7320 cells with high aspect ratio to set highAspectRatioCells
    Minimum face area = 5.18207e-10. Maximum face area = 3181.85.  Face area magnitudes OK.
    Min volume = 5.18207e-10. Max volume = 3181.85.  Total volume = 875555.  Cell volumes OK.
    Mesh non-orthogonality Max: 52.3838 average: 5.03403
    Non-orthogonality check OK.
    Face pyramids OK.
    Max skewness = 0.341413 OK.
    Coupled point location match (average 0) OK.

Failed 1 mesh checks.

End

[HPE]

Hi,

This content can help? https://www.cfd-online.com/Forums/op...4-v2006.html#6

[afa13]

Originally Posted by HPE

Hi,

This content can help? https://www.cfd-online.com/Forums/op...4-v2006.html#6

The concept is great. Thanks for helping. But can you walk me through it? i tried what you said and I got the following error:

./Allrun-parallel 
./Allrun-parallel: 18: [[: not found
Running ./Allrun.pre on /home/cfd/OpenFOAM/cfd-8/run/NACA/incompressible/simpleFoam-PLOT3D/10-aoa

# Computations for the RAS model: SpalartAllmaras

cp: cannot stat 'SpalartAllmaras.orig/system/{fvSchemes,fvSolution}': No such file or directory
./Allrun-parallel: 30: restore0Dir: not found
    ## Angle of attack = 10 [degree]
./Allrun-parallel: 56: cannot create 0/U: Directory nonexistent
Running decomposePar on /home/cfd/OpenFOAM/cfd-8/run/NACA/incompressible/simpleFoam-PLOT3D/10-aoa
Running simpleFoam in parallel on /home/cfd/OpenFOAM/cfd-8/run/NACA/incompressible/simpleFoam-PLOT3D/10-aoa using 2 processes
Running redistributePar in parallel on /home/cfd/OpenFOAM/cfd-8/run/NACA/incompressible/simpleFoam-PLOT3D/10-aoa using 2 processes
Running foamLog on /home/cfd/OpenFOAM/cfd-8/run/NACA/incompressible/simpleFoam-PLOT3D/10-aoa
    # Collecting results
mv: cannot stat '': No such file or directory
mv: cannot stat 'postProcessing': No such file or directory
mv: cannot move 'logs' to 'results/SpalartAllmaras/AoA-10/logs': Directory not empty
cp: cannot stat 'system/fv*': No such file or directory
cp: cannot stat '0': No such file or directory
./Allrun-parallel: 83: cleanTimeDirectories: not found

# Computations for the RAS model: kOmegaSST

cp: cannot stat 'kOmegaSST.orig/system/{fvSchemes,fvSolution}': No such file or directory
./Allrun-parallel: 30: restore0Dir: not found
    ## Angle of attack = 10 [degree]
./Allrun-parallel: 56: cannot create 0/U: Directory nonexistent
Running decomposePar on /home/cfd/OpenFOAM/cfd-8/run/NACA/incompressible/simpleFoam-PLOT3D/10-aoa
Running simpleFoam in parallel on /home/cfd/OpenFOAM/cfd-8/run/NACA/incompressible/simpleFoam-PLOT3D/10-aoa using 2 processes
Running redistributePar in parallel on /home/cfd/OpenFOAM/cfd-8/run/NACA/incompressible/simpleFoam-PLOT3D/10-aoa using 2 processes
Running foamLog on /home/cfd/OpenFOAM/cfd-8/run/NACA/incompressible/simpleFoam-PLOT3D/10-aoa
    # Collecting results
mv: cannot stat '': No such file or directory
mv: cannot stat 'postProcessing': No such file or directory
mv: cannot move 'logs' to 'results/kOmegaSST/AoA-10/logs': Directory not empty
cp: cannot stat 'system/fv*': No such file or directory
cp: cannot stat '0': No such file or directory
./Allrun-parallel: 83: cleanTimeDirectories: not found